复合材料加筋层合板准静态压痕实验研究及数值分析  

THE TEST AND FULL-RANGE NUMERICAL ANALYSIS OF COMPOSITE STIFFENED LAMINATES UNDER STATIC INDENTATION FORCE

作　　者：黄飞生 周仕刚[1] 宫占锋 罗腾腾[2] 薛元德[1] 

机构地区：[1]同济大学航空航天与力学学院,上海200092 [2]上海飞机设计研究院,上海200232

出　　处：《玻璃钢／复合材料》2015年第11期42-46,共5页Fiber Reinforced Plastics/Composites

摘　　要：利用ABAQUS有限元程序所建立了一种基于用户子程序USDFLD和Hashin强度准则的复合材料损伤计算模型,用该模型对复合材料加筋层合板在静压痕力作用下主要发生的纤维拉伸破坏、纤维微屈破坏、基体拉伸破坏、基体压缩破坏、层间拉伸破坏、层间压缩破坏这几种基本损伤模式进行分析。对复合材料加筋层合板在静压痕力作用下进行损伤全过程数值研究,利用该有限元模型预测复合材料层合板静压痕力作用下的荷载-位移曲线以及凹坑深度与静压痕力的关系曲线。数值仿真与实验结果吻合较好,表明该损伤模型方法的可行性。复合材料层合板加筋后拐点处的凹坑深度明显加大,达到0.84mm。通过对加筋板的刚度和强度失效规律的分析,为进一步的复合材料格栅加筋结构(如飞机结构中复合材料后压力框)的性能分析提供参考。Based on the composite stiffened laminates user subroutine USDFLD and Hashin＇s criteria, this paper damage model by using ABAQUS software. Six basic damage tion, matrix crack and matrix compression, fiber fracture and fiber crush may happen inates are under static indentation force, the damage evolution of composite stiffened presented a finite element models such as delamina- when composite stiffened lam- laminates can be simulated by this finite element damage model. Load-displacement curve and dent depth-load curve of composite laminates were predicted by the finite element composite stiffened laminates model. The computed results are in agreement with the corresponding experiment result, which proves the validity of the presented damage model. The pit depth of the com- posite stiffened laminates at the knee of curve increased obviously. Compared with unstiffened plate, the dent depth of the composite stiffened laminates came to 0. 84mm, which was considered as a visible impact damage. The method and results concluded in the paper can be useful for the performance analysis of grid-stiffened composite structure such as the rear pressure bulkhead used in aircraft.

关 键 词：复合材料加筋层合板 静压痕力 凹坑深度 Hashin准则 损伤 

分 类 号：TB332[一般工业技术—材料科学与工程]